Method and apparatus for determining blade axis position from airfoil thickness and twist angle

Abstract

The application discloses a method and device for determining a blade axis position according to a wing profile thickness and a torsion angle, the method comprising: selecting a target section according to a maximum chord section of a blade; determining suction surface maximum thickness point positions and pressure surface maximum thickness point positions of a plurality of sections in a first section of the blade according to a chord distribution curve of the blade, a relative thickness distribution curve, standard wing profile maximum thickness point positions on a suction surface and a pressure surface, and a standard wing profile relative thickness, the first section being bounded by the target section and a blade tip of the blade; calculating the blade axis positions of the plurality of sections in the first section according to relative torsion angles of the plurality of sections in the first section, the suction surface maximum thickness point positions and the pressure surface maximum thickness point positions; and calculating the blade axis positions of a plurality of sections in a second section of the blade according to blade root distances of the plurality of sections in the second section, a leading edge point position of the target section and the blade root distance of the target section, the second section being bounded by the target section and a blade root of the blade.

Description

Technical Field

[0001] This application belongs to the field of wind power generation technology, and in particular relates to a method and apparatus for determining the blade shaft position based on airfoil thickness and twist angle. Background Technology

[0002] With the development of the wind power industry, wind turbine blades are becoming longer and heavier. To minimize blade weight, continuous improvements and optimizations are needed in aerodynamics, structure, materials, and load characteristics. Among these, accurately detecting the position of the blade shaft has a significant impact on the aerodynamic shape and load of the blade.

[0003] Existing methods for determining the blade axis position are mainly based on experience. For example, the blade axis position is generally determined empirically at a distance of 30% of the chord length from the leading edge of the cross-section. At the same time, in order to ensure the smoothness of the blade's aerodynamic shape, the position of the blade axis is manually adjusted.

[0004] The problem with this method is that it ignores the thickness characteristics of the blade airfoil, leading to an excessive deviation between the location of the maximum thickness at each section of the blade and the determined blade axis position. This excessive deviation results in low structural efficiency of the main beam. Structural efficiency reflects the relationship between the material usage and structural strength of the main beam. When the structural efficiency is low, the material usage of the main beam is higher for the same structural strength requirements.

[0005] Therefore, existing methods for determining the position of the blade axis are not conducive to reducing the weight of the blade. Summary of the Invention

[0006] Therefore, this application discloses a method and apparatus for determining the blade shaft position based on airfoil thickness and twist angle, in order to reduce the weight of the blade.

[0007] The first aspect of this application provides a method for determining the blade shaft position based on airfoil thickness and twist angle, comprising:

[0008] Select the target section based on the maximum chord length of the blade;

[0009] Based on the chord length distribution curve, relative thickness distribution curve, maximum thickness point positions of the standard airfoil on the suction and pressure surfaces, and the relative thickness of the standard airfoil, determine the maximum thickness point positions of the suction surface and pressure surface of multiple cross sections in the first segment of the blade, with the target cross section and the blade tip as the boundary of the first segment;

[0010] Based on the relative rotation angles of multiple sections in the first segment, the positions of the maximum thickness points of the suction surface and the pressure surface, the blade shaft positions of multiple sections in the first segment are calculated.

[0011] For the second segment of the blade, the blade axis position of the multiple cross-sections in the second segment is calculated based on the blade root distance of the multiple cross-sections in the second segment, the leading edge position of the target cross-section, and the blade root distance of the target cross-section. The second segment is bounded by the target cross-section and the blade root.

[0012] Optionally, selecting the target section based on the maximum chord length section of the blade includes:

[0013] Select the section with the maximum chord length of the blade as the target section;

[0014] Alternatively, select a section whose distance from the maximum chord length section of the blade is a preset value as the target section.

[0015] Optionally, determining the positions of the maximum thickness points on the suction and pressure surfaces of multiple cross-sections in the first segment of the blade based on the blade's chord length distribution curve, relative thickness distribution curve, the maximum thickness points of the standard airfoil on the suction and pressure surfaces, and the relative thickness of the standard airfoil includes:

[0016] Based on the chord length distribution curve and relative thickness distribution curve of the blade, the chord length and relative thickness of multiple sections in the first segment of the blade are obtained by interpolation;

[0017] Based on the standard airfoil geometry information, determine the locations of the maximum thickness points of the standard airfoil on the suction and pressure surfaces;

[0018] Based on the chord length and relative thickness of multiple sections in the first segment, the relative thickness of the standard airfoil, and the position of the maximum thickness point of the standard airfoil on the suction and pressure surfaces, the position of the maximum thickness point of the suction surface and the position of the maximum thickness point of the pressure surface of multiple sections in the first segment are obtained by interpolation.

[0019] Optionally, the step of calculating the blade shaft position of the multiple cross-sections in the first segment based on the relative rotation angles of the multiple cross-sections in the first segment, the position of the maximum thickness point of the suction surface, and the position of the maximum thickness point of the pressure surface includes:

[0020] Based on the relative rotation angles of multiple sections in the first segment, the position of the maximum thickness point of the suction surface and the position of the maximum thickness point of the pressure surface, calculate the new thickness point positions of the suction surface and the pressure surface of multiple sections in the first segment.

[0021] Based on the new thickness points of the suction surface and the pressure surface of multiple cross sections in the first segment, the thickness position information of the suction surface and the pressure surface of multiple cross sections in the first segment are calculated.

[0022] The average position information is calculated based on the position information of the suction surface thickness and pressure surface thickness of multiple sections in the first segment;

[0023] The blade shaft positions of multiple sections in the first segment are calculated based on the average position information and the predetermined leading edge offset.

[0024] Optionally, for the second segment of the blade, calculating the blade axis position of multiple cross-sections in the second segment based on the blade root distance of multiple cross-sections in the second segment, the leading edge position of the target cross-section, and the blade root distance of the target cross-section includes:

[0025] The chord lengths of multiple sections in the second segment of the blade are obtained by interpolation based on the chord length distribution curve of the blade.

[0026] Based on the leading edge position and blade root distance of the target cross section, as well as the leading edge position and ending cross section position of the cylindrical section of the blade, the leading edge positions of multiple cross sections in the second segment are calculated.

[0027] The blade shaft positions of multiple sections in the second segment are calculated based on the leading edge point positions and chord lengths of multiple sections in the second segment.

[0028] A second aspect of this application provides an apparatus for determining the blade shaft position based on airfoil thickness and twist angle, comprising:

[0029] The selection unit is used to select the target section based on the maximum chord length section of the blade.

[0030] The determining unit is used to determine the position of the maximum thickness point of the suction surface and the position of the maximum thickness point of the pressure surface of multiple cross sections in the first segment of the blade based on the chord length distribution curve, the relative thickness distribution curve, the position of the maximum thickness point of the standard airfoil on the suction surface and the pressure surface, and the relative thickness of the standard airfoil. The first segment is bounded by the target cross section and the blade tip.

[0031] The first calculation unit is used to calculate the blade shaft position of multiple sections in the first segment based on the relative rotation angle of multiple sections in the first segment, the position of the maximum thickness point of the suction surface and the position of the maximum thickness point of the pressure surface.

[0032] The second calculation unit is used to calculate the blade axis position of multiple cross sections in the second segment based on the blade root distance of multiple cross sections in the second segment, the leading edge position of the target cross section, and the blade root distance of the target cross section. The second segment is bounded by the target cross section and the blade root.

[0033] Optionally, when the selection unit selects the target section based on the maximum chord length section of the blade, it is specifically used for:

[0034] Select the section with the maximum chord length of the blade as the target section;

[0035] Alternatively, select a section whose distance from the maximum chord length section of the blade is a preset value as the target section.

[0036] Optionally, when the determining unit determines the positions of the maximum thickness points on the suction and pressure surfaces of multiple cross-sections in the first segment of the blade based on the blade's chord length distribution curve, relative thickness distribution curve, the maximum thickness points of the standard airfoil on the suction and pressure surfaces, and the relative thickness of the standard airfoil, it is specifically used for:

[0037] Based on the chord length distribution curve and relative thickness distribution curve of the blade, the chord length and relative thickness of multiple sections in the first segment of the blade are obtained by interpolation;

[0038] Based on the standard airfoil geometry information, determine the locations of the maximum thickness points of the standard airfoil on the suction and pressure surfaces;

[0039] Based on the chord length and relative thickness of multiple sections in the first segment, the relative thickness of the standard airfoil, and the position of the maximum thickness point of the standard airfoil on the suction and pressure surfaces, the position of the maximum thickness point of the suction surface and the position of the maximum thickness point of the pressure surface of multiple sections in the first segment are obtained by interpolation.

[0040] Optionally, when the first calculation unit calculates the blade shaft position of the multiple sections in the first segment based on the relative rotation angles of the multiple sections in the first segment, the position of the maximum thickness point of the suction surface, and the position of the maximum thickness point of the pressure surface, it is specifically used for:

[0041] Based on the relative rotation angles of multiple sections in the first segment, the position of the maximum thickness point of the suction surface and the position of the maximum thickness point of the pressure surface, calculate the new thickness point positions of the suction surface and the pressure surface of multiple sections in the first segment.

[0042] Based on the new thickness points of the suction surface and the pressure surface of multiple cross sections in the first segment, the thickness position information of the suction surface and the pressure surface of multiple cross sections in the first segment are calculated.

[0043] The average position information is calculated based on the position information of the suction surface thickness and pressure surface thickness of multiple sections in the first segment;

[0044] The blade shaft positions of multiple sections in the first segment are calculated based on the average position information and the predetermined leading edge offset.

[0045] Optionally, when the second calculation unit calculates the blade axis position of multiple cross-sections in the second segment of the blade based on the blade root distance of multiple cross-sections in the second segment, the leading edge position of the target cross-section, and the blade root distance of the target cross-section, it is specifically used for:

[0046] The chord lengths of multiple sections in the second segment of the blade are obtained by interpolation based on the chord length distribution curve of the blade.

[0047] Based on the leading edge position and blade root distance of the target cross section, as well as the leading edge position and ending cross section position of the cylindrical section of the blade, the leading edge positions of multiple cross sections in the second segment are calculated.

[0048] The blade shaft positions of multiple sections in the second segment are calculated based on the leading edge point positions and chord lengths of multiple sections in the second segment.

[0049] The beneficial effects of this plan are as follows:

[0050] By combining the relative thickness distribution curve and twist angle of the blades, the blade axis position is determined, thereby reducing the deviation between the determined blade axis position of each section and the maximum thickness position of the blade. This achieves the structural efficiency of the main beam based on the blade axis position, thereby reducing the material usage of the main beam and lightening the weight of the blades without affecting the structural strength. Attached Figure Description

[0051] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of this application. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0052] Figure 1 This is a flowchart illustrating a method for determining the blade shaft position based on airfoil thickness and twist angle, as provided in an embodiment of this application.

[0053] Figure 2 This is a flowchart of another method for determining the blade shaft position based on airfoil thickness and twist angle provided in an embodiment of this application;

[0054] Figure 3 This is a schematic diagram of a blade segmentation provided in an embodiment of this application;

[0055] Figure 4 This is a schematic diagram showing the location of the maximum thickness of the i-th cross-section of a blade, provided in an embodiment of this application.

[0056] Figure 5 This is a schematic diagram of a device for determining the blade shaft position based on airfoil thickness and twist angle, provided in an embodiment of this application. Detailed Implementation

[0057] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0058] This application provides a method for determining the blade shaft position based on airfoil thickness and twist angle. Please refer to [link to relevant documentation]. Figure 1 Here is a flowchart of the method, which may include the following steps.

[0059] S101, Select the target section based on the maximum chord length section of the blade.

[0060] Optionally, the implementation of step S101 may include:

[0061] Select the section with the maximum chord length of the blade as the target section;

[0062] Alternatively, select a section whose distance from the maximum chord length section of the blade is a preset value as the target section.

[0063] For example, when determining the target section in the latter way, first determine the maximum chord length section of the blade, and then select the section 10 cm to the right of the maximum chord length (denoted as Cmax) section as the target section, or select the section 10 cm to the left of the maximum chord length section as the target section.

[0064] The above preset values ​​can be set according to actual conditions, and this embodiment does not impose any limitations.

[0065] S102. Based on the chord length distribution curve, relative thickness distribution curve, the location of the maximum thickness point of the standard airfoil on the suction and pressure surfaces, and the relative thickness of the standard airfoil, determine the location of the maximum thickness point of the suction surface and the location of the maximum thickness point of the pressure surface of multiple sections in the first segment of the blade.

[0066] The first segment is bounded by the target cross-section and the blade tip.

[0067] For example, when the target cross-section is the maximum chord length cross-section of the blade, the blade segmentation method can be found in [reference needed]. Figure 3 .

[0068] For the location of the maximum thickness point of a standard airfoil on the suction side and the location of the maximum thickness point of a standard airfoil on the pressure side, please refer to [reference needed]. Figure 4 .

[0069] The second segment is bounded by the target cross section and the blade root.

[0070] The first segment is bounded by the target cross-section and the blade tip.

[0071] For example, please see Figure 3 This is a schematic diagram of the segmentation of the blade provided in this embodiment. The cross section at a distance R1 from the blade root is the target cross section determined in S101 of this embodiment. In this example, the maximum chord length cross section of the blade is used as the target cross section.

[0072] The portion from the right side of the target cross section to the leaf tip is the first segment of the blade in this embodiment, and the portion from the left side of the target cross section to the leaf root is the second segment of the blade in this embodiment.

[0073] Figure 3 In this context, R2 represents the distance from the leaf base to the leaf tip, which can also be understood as the length of the leaf.

[0074] Optionally, a specific implementation of step S102 may include:

[0075] A1. Based on the chord length distribution curve and relative thickness distribution curve of the blade, the chord length and relative thickness of multiple sections in the first segment of the blade are obtained by interpolation.

[0076] A2. Based on the standard airfoil geometry information, determine the location of the maximum thickness point of the standard airfoil on the suction and pressure surfaces;

[0077] A3. Based on the chord length and relative thickness of multiple sections in the first segment, the relative thickness of the standard airfoil, and the position of the maximum thickness point of the standard airfoil on the suction and pressure surfaces, interpolation is used to obtain the position of the maximum thickness point of the suction surface and the position of the maximum thickness point of the pressure surface of multiple sections in the first segment.

[0078] Please see Figure 2 This is a flowchart of another method for determining the blade shaft position based on airfoil thickness and twist angle provided in this embodiment.

[0079] Step S102 of this embodiment may include... Figure 2 The process shown includes the following steps:

[0080] S1, select n cross sections.

[0081] S2, interpolation yields the chord length Ci and relative thickness RTi of section i.

[0082] S3, obtains the location of the maximum thickness point of the standard airfoil on the pressure and suction sides.

[0083] S4, interpolation is used to obtain the position of the maximum thickness point of the i-th section on the pressure surface and suction surface.

[0084] Wherein, S1 and S2 are equivalent to step A1 above, S3 is equivalent to step A2 above, and step S4 is equivalent to step A3 above.

[0085] When performing step S1, based on the aerodynamic shape of the blade, n sections can be selected one by one from the target section to the blade tip in the first segment of the blade. The distance from the selected i-th section to the blade root is denoted as Ri. The target section is denoted as the selected i-th section, and the numbering increases from the target section to the blade tip.

[0086] The distance from section i to the blade root can be measured after selecting the section, or it can be calculated based on the distance from the target section to the blade root and the rules for selecting the section.

[0087] The specific value of n can be set according to actual needs and is not limited. For example, it can be set to 10.

[0088] When selecting n sections, they can be selected at equal intervals, i.e., according to the rule that the distance between any two sections on the r-axis is equal, or they can be selected according to other rules, without any limitation.

[0089] In step S2, the chord length Ci and relative thickness RTi of each section i in the selected n sections can be interpolated based on the known blade chord length distribution curve and relative thickness distribution curve.

[0090] Among them, the blade chord length distribution curve and the relative thickness distribution curve are pre-defined curves. The blade chord length distribution curve reflects the relationship between the chord length of any section on the blade and the distance R from that section to the blade root, while the relative thickness distribution curve reflects the relationship between the relative thickness of any section on the blade and the distance R from that section to the blade root.

[0091] Therefore, in S2, for any selected section i, its distance Ri from the blade root can be substituted into the blade chord length distribution curve, and the chord length Ci of section i can be determined based on the correlation represented by the curve. Similarly, the distance Ri from section i to the blade root can be substituted into the relative thickness distribution curve, and the relative thickness RTi of section i can be determined based on the correlation represented by the curve.

[0092] In step S3, the geometric shape of the standard airfoil of the current blade can be determined first, that is, the profile of the maximum chord length section of the current blade. Based on this shape, the location of the maximum thickness point of the suction surface corresponding to this geometric shape is found from the standard airfoil data table. That is, the y-direction position of the suction surface point on the geometric shape of the standard airfoil that is farthest from the chord line. In this embodiment, the locations of the maximum thickness points of the suction surface on the geometric shape of the standard airfoil are denoted as ya_ss and xa_ss.

[0093] The directions of the y-axis and x-axis can be found in [reference]. Figure 4 .

[0094] Similar to the location of the maximum thickness point of the suction surface, the location of the maximum thickness point of the pressure surface corresponding to the standard airfoil geometry of the current blade can be obtained by looking up a table. This is the y-axis position of the pressure surface point on the standard airfoil geometry that is furthest from the chord line. In this embodiment, the location of the maximum thickness point of the pressure surface on the standard airfoil geometry is denoted as ya_ps and xa_ps.

[0095] In step S4, for the selected i-th section, the maximum thickness points of the suction surface of the i-th section, yi_ss and xi_ss, can be obtained by interpolation based on the relative thickness RTi of the i-th section, the relative thickness of the standard airfoil, and the location of the maximum thickness point of the standard airfoil. The maximum thickness points of the pressure surface of the i-th section, yi_ps and xi_ps, can also be obtained.

[0096] The locations of the maximum thickness points of the i-th cross-section on the suction surface and on the pressure surface can be found in [reference]. Figure 4 .

[0097] The relative thickness of a standard airfoil can be understood as the relative thickness of the blade's maximum chord length section. This data can be obtained by consulting a standard airfoil data table based on the airfoil's geometry. In this embodiment, the relative thickness of the standard airfoil can be denoted as RT0.

[0098] For the selected i-th section, the position of the maximum thickness point ya_ss of the standard airfoil on the suction surface, the relative thickness RT0 of the standard airfoil, and the relative thickness RTi of the i-th section can be substituted into the following formula to calculate the position of the maximum thickness point of the suction surface of the i-th section:

[0099] ya_ss / relative thickness of standard airfoil RT0*RTi=yi_ss.

[0100] Similarly, by substituting the x-coordinate of the maximum thickness point of the standard airfoil on the suction surface, the relative thickness RT0 of the standard airfoil, and the relative thickness RTi of the i-th section into the following formula, the x-coordinate of the maximum thickness point of the suction surface on the i-th section can be calculated:

[0101] xa_ss / relative thickness of standard airfoil RT0*RTi=xi_ss.

[0102] For the selected i-th section, the location of the maximum thickness point ya_ps of the standard airfoil on the pressure surface, the relative thickness RT0 of the standard airfoil, and the relative thickness RTi of the i-th section can be substituted into the following formula to calculate the location of the maximum thickness point of the pressure surface of the i-th section:

[0103] ya_ps / relative thickness of standard airfoil RT0*RTi=yi_ps.

[0104] Similarly, by substituting the x-axis coordinate of the maximum thickness point of the standard airfoil on the pressure surface, the relative thickness RT0 of the standard airfoil, and the relative thickness RTi of the i-th section into the following formula, the x-axis coordinate of the maximum thickness point of the pressure surface on the i-th section can be calculated:

[0105] xa_ps / relative thickness of standard airfoil RT0*RTi=xi_ps.

[0106] S103. Based on the relative rotation angles of multiple sections in the first segment, the position of the maximum thickness point of the suction surface and the position of the maximum thickness point of the pressure surface, the blade shaft position of multiple sections in the first segment is calculated.

[0107] Optionally, a specific implementation of step S103 may include:

[0108] B1. Based on the relative rotation angles of multiple sections in the first segment, the position of the maximum thickness point of the suction surface and the position of the maximum thickness point of the pressure surface, calculate the new thickness point positions of the suction surface and the pressure surface of multiple sections in the first segment.

[0109] B2. Based on the new thickness points of the suction surface and the pressure surface of multiple cross-sections in the first segment, calculate the thickness position information of the suction surface and the pressure surface of multiple cross-sections in the first segment.

[0110] B3, the average position information is calculated based on the position information of the suction surface thickness and pressure surface thickness of multiple sections in the first segment;

[0111] B4. The blade shaft positions of multiple sections in the first segment are calculated based on the average position information and the predetermined leading edge offset.

[0112] Leading edge offset refers to the offset of the maximum thickness point relative to the leading edge of the blade shaft. For the meaning of leading edge offset, please refer to [link to relevant documentation]. Figure 4 .

[0113] Step S103 in this embodiment can be equivalent to Figure 2 Steps S5 to S10 of the process shown:

[0114] S5, determine the angle of the leaf root parting surface and the relative rotation angle of the i-th section.

[0115] S6, calculate the new thickness point positions yi_ps_new and yi_ss_new for each section.

[0116] S7, calculate Ki_ps and Ki_ss for each section.

[0117] S8, calculate the average value of Ki for n cross sections.

[0118] S9 determines the leading edge offset L_disp of the point with the maximum thickness.

[0119] S10, calculate the blade axis position of section i.

[0120] Steps S5 and S6 are equivalent to step B1 above, step S7 is equivalent to step B2 above, step B6 is equivalent to step B3 above, and steps B9 and B10 are equivalent to step B4 above.

[0121] Where yi_ps_new is equivalent to the new thickness point of section i on the pressure surface, and yi_ss_new is equivalent to the new thickness point of section i on the suction surface.

[0122] Ki_ps is equivalent to the pressure surface thickness and location information of section i, and Ki_ss is equivalent to the suction surface thickness and location information of section i.

[0123] In step S5, the angle Tref of the blade root parting surface can be determined first. This parameter can be obtained by measuring the blade. Then, for each section i, the angle Ti of that section can be measured. Finally, based on the angle Ti of section i and the angle Tref of the blade root parting surface, the relative rotation angle roti of section i can be calculated using the following formula:

[0124] roti = Ti - Tref.

[0125] In step S6, for each section i of the first segment, the relative rotation angle of section i and the position of the maximum thickness point of the pressure surface of section i can be substituted into the following formula to calculate the new thickness point position yi_ps_new of the pressure surface of section i:

[0126] yi_ps_new=xi_ps*sin(roti)+yi_ps*cos(roti).

[0127] Similarly, for each section i, the relative rotation angle of section i and the position of the maximum thickness point of the suction surface of section i can be substituted into the following formula to calculate the position of the new thickness point yi_ss_new of the suction surface of section i:

[0128] yi_ss_new=xi_ss*sin(roti)+yi_ss*cos(roti).

[0129] In step S7, for each section i of the first segment, the pressure surface thickness location information Ki_ps of that section can be calculated using the following formula:

[0130] Ki_ps=(Dr-2*yi_ps_new*Ci) / (2*(Ri-R1)).

[0131] Where Ri is the distance from the i-th cross section to the leaf root, R1 is the distance from the target cross section to the leaf root, and Dr is the diameter of the leaf root.

[0132] For each section i in the first segment, the suction surface thickness and location information Ki_ss can be calculated using the following formula:

[0133] Ki_ss=(Dr-2*yi_ss_new*Ci) / (2*(Ri-R1)).

[0134] In step S8, the average position information, which is the aforementioned Ki average, can be calculated using the following formula, denoted as K_ave:

[0135]

[0136] In step S9, the leading edge offset L_disp can be calculated according to the following formula:

[0137] L_disp = Dr / 2*b.

[0138] b is a preset constant, which can generally be selected within the range of greater than 0 and less than or equal to 0.2.

[0139] The purpose of determining the leading edge offset is to ensure that there is a certain distance between the blade shaft and the leading edge line of the blade, so that the main load-bearing component of the blade, the beam cap, can be properly installed into the blade.

[0140] In step S10, for each section i of the first segment, the blade shaft position of that section can be calculated using the following formula:

[0141] (Dr-K_ave*(2*(Ri-R1))) / (2*Ci)+L_disp / Ci.

[0142] S104, for the second segment of the blade, the blade axis position of multiple sections in the second segment is calculated based on the blade root distance of multiple sections in the second segment, the leading edge position of the target section, and the blade root distance of the target section.

[0143] Optionally, a specific implementation of S104 may include:

[0144] C1, the chord lengths of multiple sections in the second segment of the blade are obtained by interpolation based on the chord length distribution curve of the blade;

[0145] C2, based on the leading edge position and blade root distance of the target section, as well as the leading edge position and ending section position of the cylindrical section of the blade, the leading edge position of multiple sections in the second segment is calculated;

[0146] C3, the blade shaft positions of multiple sections in the second segment are calculated based on the leading edge point positions and chord lengths of multiple sections in the second segment.

[0147] Step S104 in this embodiment can be equivalent to Figure 2 Steps S11 to S16 of the process shown:

[0148] S11, select m cross-sections.

[0149] S12, interpolation yields the chord length Ci of section i.

[0150] S13, determine the end section position R0 and the leading edge position y0 of the cylindrical segment.

[0151] S14, determine the leading edge point position yref of the target section and the corresponding section position Rref.

[0152] S15, determine the y-direction position of the i-th section.

[0153] S16, calculate the blade shaft position of the i-th section.

[0154] Wherein, steps S11 and S12 are equivalent to step C1 above, steps S13 to S15 are equivalent to step C2 above, and step S16 is equivalent to step C3 above.

[0155] The method of selecting m cross-sections in step S11 can be the same as the method of selecting n cross-sections in step S1, and will not be repeated here.

[0156] The value of m can be equal to or less than n. The specific value is determined based on the actual situation and is not limited.

[0157] In step S12, the distance Ri from each section i to the leaf root in the above m sections can be determined first. The method of determination is the same as the method of determining the distance from the section to the leaf root in the first section, and will not be repeated here.

[0158] Then, for each section i among the m sections, its distance Ri from the leaf root is substituted into the predetermined chord length distribution curve for interpolation calculation, thereby obtaining the chord length Ci of that section.

[0159] In step S13, the position R0 of the end section of the cylindrical blade segment can be determined by measurement, that is, the distance from the end section of the cylindrical blade segment to the blade root, and the position y0 of the leading edge point of the end section of the cylindrical blade segment.

[0160] Wherein, y0 can be calculated according to the formula after measuring the leaf root diameter Dr: y0=Dr / 2.

[0161] In step S14, the position yref and distance Rref of the leading edge of the target section can be obtained as follows:

[0162] First, along Figure 3 The distance from the target section to the blade root is measured along the R-axis, as shown, to obtain the blade root distance (also known as the section position) Rref of the target section. Then, the y-direction position yref of the leading edge point of the target section is calculated using the following formula:

[0163] yref = Dr / 2 + L_disp.

[0164] In step S15, for each section i of the second segment, the distance Ri from that section to the leaf root can be substituted into the following formula to obtain the y-position yi of the i-th section in the second segment:

[0165] yi=(yref-y0) / (Rref-R0)*(Ri-R0)+y0.

[0166] In step S16, for any section i among the m sections of the second segment, the blade shaft position of that section can be calculated according to the formula based on the y-direction position yi of the leading edge point of that section and the chord length Ci of that section:

[0167] yi / Ci.

[0168] Thus, this scheme has determined the blade axis positions of several cross sections in the first and second segments of the blade. When it is necessary to lay the main beam in the blade, on the one hand, a curve representing the blade axis can be fitted based on the blade axis positions of each cross section, and the shape of the blade main beam can be designed based on this curve. On the other hand, during the laying of the main beam, the position of the main beam at each cross section of the first and second segments can be checked in a timely manner to ensure that it is consistent with the blade axis position at that cross section, so as to ensure that the blade main beam is laid according to the position of the blade axis.

[0169] The beneficial effects of this plan are as follows:

[0170] By combining the relative thickness distribution curve and twist angle of the blades, the blade axis position is determined, thereby reducing the deviation between the determined blade axis position of each section and the maximum thickness position of the blade. This achieves the structural efficiency of the main beam based on the blade axis position, thereby reducing the material usage of the main beam and lightening the weight of the blades without affecting the structural strength.

[0171] On the other hand, existing detection methods, after initially determining the position of the blade shaft based on experience, still require manual adjustment of the blade shaft position, which is a time-consuming process. In contrast, the detection method provided in this embodiment can directly calculate the position of the blade shaft using relevant blade data, eliminating the need for manual adjustment and shortening the time required to determine the blade shaft position.

[0172] According to the method for determining the blade shaft position based on airfoil thickness and twist angle provided in the embodiments of this application, the embodiments of this application also provide an apparatus for determining the blade shaft position based on airfoil thickness and twist angle. Please refer to [link to relevant documentation]. Figure 5 This is a schematic diagram of the structure of the device, which may include the following units.

[0173] Selection unit 501 is used to select the target section based on the maximum chord length section of the blade;

[0174] The determining unit 502 is used to determine the position of the maximum thickness point of the suction surface and the position of the maximum thickness point of the pressure surface of multiple sections in the first segment of the blade based on the chord length distribution curve, the relative thickness distribution curve, the position of the maximum thickness point of the standard airfoil on the suction surface and the pressure surface, and the relative thickness of the standard airfoil. The first segment is bounded by the target section and the blade tip.

[0175] The first calculation unit 503 is used to calculate the blade shaft position of multiple sections in the first segment based on the relative rotation angle of multiple sections in the first segment, the position of the maximum thickness point of the suction surface and the position of the maximum thickness point of the pressure surface.

[0176] The second calculation unit 504 is used to calculate the blade axis position of multiple sections in the second segment of the blade based on the blade root distance of multiple sections in the second segment, the leading edge position of the target section, and the blade root distance of the target section. The second segment is bounded by the target section and the blade root.

[0177] Optionally, when selecting the target section based on the maximum chord length section of the blade, the selection unit 501 is specifically used for:

[0178] Select the section with the maximum chord length of the blade as the target section;

[0179] Alternatively, select a section whose distance from the maximum chord length section of the blade is a preset value as the target section.

[0180] Optionally, when determining the positions of the maximum thickness points on the suction and pressure surfaces of multiple sections in the first segment of the blade based on the blade's chord length distribution curve, relative thickness distribution curve, the maximum thickness points of the standard airfoil on the suction and pressure surfaces, and the relative thickness of the standard airfoil, the determining unit 502 is specifically used for:

[0181] Based on the chord length distribution curve and relative thickness distribution curve of the blade, the chord length and relative thickness of multiple sections in the first segment of the blade are obtained by interpolation.

[0182] Based on the standard airfoil geometry information, determine the locations of the maximum thickness points of the standard airfoil on the suction and pressure surfaces;

[0183] Based on the chord length and relative thickness of multiple sections in the first segment, the relative thickness of the standard airfoil, and the location of the maximum thickness point of the standard airfoil on the suction and pressure surfaces, the location of the maximum thickness point of the suction surface and the location of the maximum thickness point of the pressure surface of multiple sections in the first segment are obtained by interpolation.

[0184] Optionally, when the first calculation unit 503 calculates the blade shaft position of multiple sections in the first segment based on the relative rotation angles of multiple sections in the first segment, the position of the maximum thickness point of the suction surface, and the position of the maximum thickness point of the pressure surface, it is specifically used for:

[0185] Based on the relative rotation angles of multiple sections in the first segment, the location of the maximum thickness point of the suction surface and the location of the maximum thickness point of the pressure surface, calculate the new thickness point locations of the suction surface and the pressure surface of multiple sections in the first segment.

[0186] Based on the new thickness points of the suction surface and the pressure surface of multiple cross-sections in the first segment, the position information of the suction surface thickness and the position information of the pressure surface thickness of multiple cross-sections in the first segment are calculated.

[0187] The average position information is calculated based on the position information of the suction surface thickness and pressure surface thickness of multiple sections in the first segment;

[0188] The blade shaft positions of multiple sections in the first segment are calculated based on the average position information and the pre-determined leading edge offset.

[0189] Optionally, the second calculation unit 504, for the second segment of the blade, calculates the blade axis position of multiple sections in the second segment based on the blade root distance, the leading edge position of the target section, and the blade root distance of the target section. Specifically, this is used for:

[0190] The chord lengths of multiple sections in the second segment of the blade are obtained by interpolation based on the chord length distribution curve of the blade.

[0191] Based on the leading edge position and blade root distance of the target section, as well as the leading edge position and ending section position of the cylindrical section of the blade, the leading edge positions of multiple sections in the second segment are calculated.

[0192] The blade shaft positions of multiple sections in the second segment are calculated based on the leading edge point positions and chord lengths of multiple sections in the second segment.

[0193] The specific working principle and beneficial effects of the device for determining the blade shaft position based on airfoil thickness and twist angle provided in this embodiment can be found in the relevant steps and beneficial effects of the method for determining the blade shaft position based on airfoil thickness and twist angle provided in the embodiments of this application, and will not be repeated here.

[0194] It should be noted that the various embodiments in this specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.

[0195] For ease of description, the above systems or devices are described separately as various modules or units based on their functions. Of course, in implementing this application, the functions of each unit can be implemented in one or more software and / or hardware components.

[0196] As can be seen from the above description of the embodiments, those skilled in the art can clearly understand that this application can be implemented by means of software plus necessary general-purpose hardware platforms. Based on this understanding, the technical solution of this application, in essence, or the part that contributes to the prior art, can be embodied in the form of a software product. This computer software product can be stored in a storage medium, such as ROM / RAM, magnetic disk, optical disk, etc., and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute the methods described in various embodiments or some parts of the embodiments of this application.

[0197] Finally, it should be noted that in this document, relational terms such as first, second, third, and fourth are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0198] The above description is only a preferred embodiment of this application. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the principle of this application, and these improvements and modifications should also be considered within the scope of protection of this application.

Claims

1. A method for determining the blade shaft position based on airfoil thickness and twist angle, characterized in that, include: Select the target section based on the maximum chord length of the blade; Based on the chord length distribution curve and relative thickness distribution curve of the blade, the chord length and relative thickness of multiple cross sections in the first segment of the blade are obtained by interpolation, wherein the first segment is bounded by the target cross section and the blade tip. Based on the standard airfoil geometry information, determine the locations of the maximum thickness points of the standard airfoil on the suction and pressure surfaces; Based on the chord length and relative thickness of multiple sections in the first segment, the relative thickness of the standard airfoil, and the position of the maximum thickness point of the standard airfoil on the suction and pressure surfaces, the position of the maximum thickness point of the suction surface and the position of the maximum thickness point of the pressure surface of multiple sections in the first segment are obtained by interpolation. Based on the relative rotation angles of multiple sections in the first segment, the position of the maximum thickness point of the suction surface and the position of the maximum thickness point of the pressure surface, calculate the new thickness point positions of the suction surface and the pressure surface of multiple sections in the first segment. Based on the new thickness points of the suction surface and the pressure surface of multiple cross sections in the first segment, the thickness position information of the suction surface and the pressure surface of multiple cross sections in the first segment are calculated. The average position information is calculated based on the position information of the suction surface thickness and pressure surface thickness of multiple sections in the first segment; The blade shaft positions of multiple sections in the first segment are calculated based on the average position information and the predetermined leading edge offset. For the second segment of the blade, the blade axis position of the multiple cross-sections in the second segment is calculated based on the blade root distance of the multiple cross-sections in the second segment, the leading edge position of the target cross-section, and the blade root distance of the target cross-section. The second segment is bounded by the target cross-section and the blade root.

2. The method according to claim 1, characterized in that, The step of selecting the target section based on the maximum chord length section of the blade includes: Select the section with the maximum chord length of the blade as the target section; Alternatively, select a section whose distance from the maximum chord length section of the blade is a preset value as the target section.

3. The method according to claim 1, characterized in that, For the second segment of the blade, the blade axis position of multiple cross-sections in the second segment is calculated based on the blade root distance of multiple cross-sections in the second segment, the leading edge position of the target cross-section, and the blade root distance of the target cross-section, including: The chord lengths of multiple sections in the second segment of the blade are obtained by interpolation based on the chord length distribution curve of the blade. Based on the leading edge position and blade root distance of the target cross section, as well as the leading edge position and ending cross section position of the cylindrical section of the blade, the leading edge positions of multiple cross sections in the second segment are calculated. The blade shaft positions of multiple sections in the second segment are calculated based on the leading edge point positions and chord lengths of multiple sections in the second segment.

4. A device for determining the blade shaft position based on airfoil thickness and twist angle, characterized in that, include: The selection unit is used to select the target section based on the maximum chord length section of the blade. Determine the unit, used for: Based on the chord length distribution curve and relative thickness distribution curve of the blade, the chord length and relative thickness of multiple cross sections in the first segment of the blade are obtained by interpolation, wherein the first segment is bounded by the target cross section and the blade tip. Based on the standard airfoil geometry information, determine the locations of the maximum thickness points of the standard airfoil on the suction and pressure surfaces; Based on the chord length and relative thickness of multiple sections in the first segment, the relative thickness of the standard airfoil, and the position of the maximum thickness point of the standard airfoil on the suction and pressure surfaces, the position of the maximum thickness point of the suction surface and the position of the maximum thickness point of the pressure surface of multiple sections in the first segment are obtained by interpolation. The first computing unit is used for: Based on the relative rotation angles of multiple sections in the first segment, the position of the maximum thickness point of the suction surface and the position of the maximum thickness point of the pressure surface, calculate the new thickness point positions of the suction surface and the pressure surface of multiple sections in the first segment. Based on the new thickness points of the suction surface and the pressure surface of multiple cross sections in the first segment, the thickness position information of the suction surface and the pressure surface of multiple cross sections in the first segment are calculated. The average position information is calculated based on the position information of the suction surface thickness and pressure surface thickness of multiple sections in the first segment; The blade shaft positions of multiple sections in the first segment are calculated based on the average position information and the predetermined leading edge offset. The second calculation unit is used to calculate the blade axis position of multiple cross sections in the second segment based on the blade root distance of multiple cross sections in the second segment, the leading edge position of the target cross section, and the blade root distance of the target cross section. The second segment is bounded by the target cross section and the blade root.

5. The apparatus according to claim 4, characterized in that, When the selection unit selects the target section based on the maximum chord length section of the blade, it is specifically used for: Select the section with the maximum chord length of the blade as the target section; Alternatively, select a section whose distance from the maximum chord length section of the blade is a preset value as the target section.

6. The apparatus according to claim 4, characterized in that, The second calculation unit, for the second segment of the blade, calculates the blade axis position of multiple sections in the second segment based on the blade root distance of multiple sections in the second segment, the leading edge position of the target section, and the blade root distance of the target section. Specifically, it is used for: The chord lengths of multiple sections in the second segment of the blade are obtained by interpolation based on the chord length distribution curve of the blade. Based on the leading edge position and blade root distance of the target cross section, as well as the leading edge position and ending cross section position of the cylindrical section of the blade, the leading edge positions of multiple cross sections in the second segment are calculated. The blade shaft positions of multiple sections in the second segment are calculated based on the leading edge point positions and chord lengths of multiple sections in the second segment.

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